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    METHOD FOR COOLING TURBINE SECTION OF ROTATING MACHINE
    1.
    发明专利
    METHOD FOR COOLING TURBINE SECTION OF ROTATING MACHINE 失效

    公开(公告)号：JP2001059402A

    公开(公告)日：2001-03-06

    申请号：JP2000233873

    申请日：2000-08-02

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MERRY BRIAN

    IPC: F01D9/02 ,  F01D5/18 ,  F01D11/00

    Abstract: PROBLEM TO BE SOLVED: To provide a method for efficiently cooling the stator vane of a rotating machine. SOLUTION: In this method for cooling a rotating machine having platforms of adjacent stator vanes 46a, 46b respectively including in their tailing edge regions a meandered channel for cooling the platforms, cooling fluid is introduced to a backmost final leg part in the channel and is introduced to the lateral direction of the backmost leg part, from whose direction a cooling fluid stream is formed including at least 30% of a flow which is led to flow into the channel and is collided with the negative pressure side surfaces 136a, 136b of the adjacent vanes.

    COOLABLE STATOR VANE FOR ROTATING MACHINE
    2.
    发明专利
    COOLABLE STATOR VANE FOR ROTATING MACHINE 失效

    公开(公告)号：JP2001065306A

    公开(公告)日：2001-03-13

    申请号：JP2000233872

    申请日：2000-08-02

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ZELESKY MARK F ,  STEUBER GARY D ,  KANE DANIEL E ,  MERRY BRIAN

    IPC: F01D9/02 ,  F01D5/18 ,  F01D9/04

    Abstract: PROBLEM TO BE SOLVED: To provide a comparatively simple cooling flow passage for rear end area of a stator vane. SOLUTION: A platform for the stator vane includes a meandering flow passage 168 for cooling fluid including two paths 169, 170 provided in the rear end area of the vane. The meandering flow passage 168 extends to a side, folds back and makes flow flowing backward. An endmost part of the meandering flow passage 168 is adjacent to the rear end 134 so as to accept at least the half flow flowing into the flow passage 168 and to discharge the flow through a gas flow passage surface and the rear end 134 of the platform.

    REINFORCEMENT RINGS FOR A DIFFUSER SECTION OF A TIP TURBINE ENGINE FAN ROTOR ASSEMBLY
    4.
    发明申请
    REINFORCEMENT RINGS FOR A DIFFUSER SECTION OF A TIP TURBINE ENGINE FAN ROTOR ASSEMBLY 审中-公开
    用于提升涡轮发动机风扇转子总成的增压器部分的加固环

    公开(公告)号：WO2007015916A3

    公开(公告)日：2007-04-05

    申请号：PCT/US2006028122

    申请日：2006-07-20

    Applicant: UNITED TECHNOLOGIES CORP ,  NORRIS JAMES W ,  NORDEEN CRAIG A ,  ROBERGE GARY ,  MERRY BRIAN

    Inventor： NORRIS JAMES W ,  NORDEEN CRAIG A ,  ROBERGE GARY ,  MERRY BRIAN

    IPC: F02K3/068 ,  F01D5/30 ,  F02C3/073 ,  F04D25/04

    CPC classification number: F04D29/541 ,  F01D5/022 ,  F02C3/073 ,  F02K3/068 ,  F05D2300/702 ,  Y02T50/672

    Abstract: A fan-turbine rotor assembly (24) includes a diffuser (114) mountable to the outer periphery of a multitude of hollow fan blade sections (72) to provide structural support to the outer tips of the fan blade sections and to turn and diffuse the airflow from the radial core airflow passage toward an axial airflow direction. The diffuser includes a fan blade tip shroud inner portion (136) which forms a planar ring about the multiple of fan blade sections. Diffuser support rings (115a, 115b) are mounted to the fan blade tip shroud to further share the radial load applied to the fan blade sections by the blade mounted diffuser and annular turbine (32).

    Abstract translation: 风扇涡轮机转子组件（24）包括可安装到多个中空风扇叶片部分（72）的外周的扩散器（114），以向风扇叶片部分的外部尖端提供结构支撑，并且使 从径向芯气流通道朝向轴向气流方向的气流。 扩散器包括风扇叶片尖端护罩内部部分（136），其围绕多个风扇叶片部分形成平面环。 扩散器支撑环（115a，115b）安装到风扇叶片尖端护罩，以进一步共享由叶片安装的扩散器和环形涡轮机（32）施加到风扇叶片部分的径向载荷。

    STACKED ANNULAR COMPONENTS FOR TURBINE ENGINES
    6.
    发明申请
    STACKED ANNULAR COMPONENTS FOR TURBINE ENGINES 审中-公开
    用于涡轮发动机的堆叠式环形构件

    公开(公告)号：WO2006110125A3

    公开(公告)日：2007-02-22

    申请号：PCT/US2004040206

    申请日：2004-12-01

    Applicant: UNITED TECHNOLOGIES CORP ,  SUCIU GABRIEL L ,  ROBERGE GARY D ,  MERRY BRIAN

    Inventor： SUCIU GABRIEL L ,  ROBERGE GARY D ,  MERRY BRIAN

    IPC: F01D5/34 ,  F01D5/02 ,  F01D5/06 ,  F02C3/073 ,  F02K3/068

    CPC classification number: F02K3/068 ,  F01D5/025 ,  F01D5/34 ,  F02C3/067 ,  F02C3/073 ,  Y02T50/671 ,  Y10T29/49321

    Abstract: Improved annular components and improved methods for assembling annular components into a turbine engine are described with respect to an axial compressor having a plurality of annular compressor rotor airfoil assemblies (120) as an example. Each compressor rotor airfoil assembly comprises an annular rotor portion (122), a spacer portion (124) extending axially therefrom and a plurality of airfoils (52) extending radially thereform. The plurality of airfoils may be integrally formed with the annular portion. The compressor rotor airfoil assemblies are stacked sequentially on a center-tie (134) or outer circumferential tie. The spacer portion of one compressor rotor airfoil assembly (120a) abuts the annular rotor portion of the adjacent compressor rotor airfoil assembly (120b) to retain one another on the center-tied outer circumferential tie. By stacking the compressor rotor airfoil assemblies sequentially and then retaining them, the typical split cases, flanges and rotor bolts may be eliminated.

    Abstract translation: 作为示例，关于具有多个环形压缩机转子翼型组件（120）的轴向压缩机来描述改进的环形部件和用于将环形部件组装到涡轮发动机中的改进方法。 每个压缩机转子翼型组件包括环形转子部分（122），从其轴向延伸的间隔部分（124）和沿径向延伸的多个翼型件（52）。 多个翼型件可以与环形部分一体地形成。 压缩机转子翼型件组件依次堆叠在中心连接件（134）或外圆环上。 一个压缩机转子翼型组件（120a）的间隔部分邻接邻近的压缩机转子翼型组件（120b）的环形转子部分，以将它们彼此保持在中心连接的外圆环上。 通过依次堆叠压缩机转子叶片组件然后保持它们，可以消除典型的分体式壳体，凸缘和转子螺栓。

    ANNULAR TURBINE RING ROTOR
    7.
    发明申请
    ANNULAR TURBINE RING ROTOR 审中-公开
    环形涡轮机转子

    公开(公告)号：WO2006059997A3

    公开(公告)日：2006-11-16

    申请号：PCT/US2004040125

    申请日：2004-12-01

    Applicant: UNITED TECHNOLOGIES CORP ,  SUCIU GABRIEL L ,  NORRIS JAMES W ,  NORDEEN CRAIG A ,  MERRY BRIAN

    Inventor： SUCIU GABRIEL L ,  NORRIS JAMES W ,  NORDEEN CRAIG A ,  MERRY BRIAN

    IPC: F01D5/30 ,  F01D11/02

    CPC classification number: F01D11/02 ,  F01D5/30

    Abstract: A fan-turbine rotor assembly (24) includes one or more turbine ring rotors (32). Each turbine ring rotor is cast as a single integral annular ring. By forming the turbine as one or more rings, leakage between adjacent blade platforms is minimized which increases engine efficiency. Assembly of the turbine ring rotors to the diffuser ring (114) includes axial installation and radial locking of each turbine ring rotor.

    Abstract translation: 风扇 - 涡轮转子组件（24）包括一个或多个涡轮环转子（32）。 每个涡轮机环形转子都被铸造为一个整体的环形环。 通过将涡轮机形成为一个或多个环，相邻的叶片平台之间的泄漏被最小化，这提高了发动机效率。 涡轮环转子到扩散器环（114）的组装包括每个涡轮环转子的轴向安装和径向锁定。

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